EP1134422A2 - Procédé pour le contrôle de pompage d' un turbo-compresseur - Google Patents

Procédé pour le contrôle de pompage d' un turbo-compresseur Download PDF

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Publication number
EP1134422A2
EP1134422A2 EP01104340A EP01104340A EP1134422A2 EP 1134422 A2 EP1134422 A2 EP 1134422A2 EP 01104340 A EP01104340 A EP 01104340A EP 01104340 A EP01104340 A EP 01104340A EP 1134422 A2 EP1134422 A2 EP 1134422A2
Authority
EP
European Patent Office
Prior art keywords
control
control valve
valve
controller
pressure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP01104340A
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German (de)
English (en)
Other versions
EP1134422B1 (fr
EP1134422A3 (fr
Inventor
Wilfried Dr. Blotenberg
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN Energy Solutions SE
Original Assignee
MAN Turbomaschinen AG
MAN Turbo GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MAN Turbomaschinen AG, MAN Turbo GmbH filed Critical MAN Turbomaschinen AG
Publication of EP1134422A2 publication Critical patent/EP1134422A2/fr
Publication of EP1134422A3 publication Critical patent/EP1134422A3/fr
Application granted granted Critical
Publication of EP1134422B1 publication Critical patent/EP1134422B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids

Definitions

  • the invention relates to a method for protecting a Turbocompressor before operation in an unstable work area the features of the preamble of claim 1.
  • the known prior art deals with measures whose goal is to shift the working point early in the direction of the surge limit and react proactively.
  • Other measures have that Aim to linearize nonlinearities of the control loop in order to optimal response behavior of the Get control system.
  • EP-PS 335 105 a method is described which by measuring a process disturbance as close as possible to Place of origin, that is as far as possible from Turbo compressor to detect a malfunction and move towards it react.
  • This patent assumes that a malfunction on Place of origin can be measured earlier than on Turbo compressor itself and that thereby a lead time arises, which has a positive effect on the control behavior.
  • this patent also uses the measurement data close to The place of origin of the disturbance is only to justify it treat like the measurands directly on the turbo compressor be measured.
  • the measured variables are closed Control loop used.
  • this method has the disadvantage that it needs a deviation to change the Effect.
  • the invention has for its object the generic To design procedures in such a way that the unstable state of the Turbocompressor recorded and corrected more quickly and safely can be.
  • the essential idea of the invention is from a flow measurement to the process as dense as possible to calculate a size in the process that future flow through the turbo compressor and derive a correction quantity from this measurement quantity the surge limit control valve of the turbo compressor is actuated directly. This way it becomes possible to protect the Turbo compressor before operating in the unstable The surge limit control valve with foresight to open.
  • FIG. 1 An embodiment of the invention is in the drawing shown and is explained in more detail below.
  • the Drawing shows the flow diagram of a method for protection of a turbo compressor before operation in the unstable Workspace.
  • a pipeline 1 is turned on via a fuel gas line 2 Fuel gas removed, in a turbo compressor 3 of z. B. 25 bar pipeline pressure compressed to a pressure of 52 bar and Via a discharge line 4 to a gas turbine 5. In front Entry into the gas turbine 5 is in the discharge line 4 Fuel gas control valve 6 is provided.
  • this suction pressure control valve 10 With a strongly fluctuating inlet pressure, the turbo compressor 3, a suction pressure control valve 10 in the fuel gas line 2 upstream.
  • the task of this suction pressure control valve 10 consists of one with fluctuating pipeline pressure Suction pressure regulator 11 a constant inlet pressure for the Maintain turbo compressor 3.
  • the compressor outlet pressure is controlled by a final pressure regulator 20 regulated to constant values by the Compressor inlet guide vanes 21 via an actuator 22 be adjusted.
  • the final pressure is measured using a pressure sensor measured and transmitted via a signal line 23. Due to the design, they can Compressor inlet guide vanes 21 within 15 to 60 Run through the entire actuating stroke for seconds.
  • the pipeline pressure should be above the required Gas turbine inlet pressure can rise is one Bypass line 7 which bypasses the turbo compressor 3 and in which a bypass valve 8 is arranged. About these Bypass line 7, the gas turbine 5 bypassing the Turbo compressor 3 can be supplied directly with fuel gas if the pipeline pressure above the required and by the Turbo compressor 3 generated compressor outlet pressure is.
  • the bypass valve 8 is with a bypass pressure regulator 9 connected.
  • One of the discharge line 4 is behind the turbo compressor 3 Umblasetechnisch 12 branched into the fuel gas line 2 before is returned to the turbo compressor 3.
  • Umblase effet 12 branched into the fuel gas line 2 before is returned to the turbo compressor 3.
  • a blow-off or surge limit control valve 13 is arranged, that via a control line 14 with a surge limit controller 15 connected is. Fuel gas can be supplied via this blow-by line 12 Blown suction side of the turbo compressor 3.
  • a temperature sensor for detecting the intake temperature T A of the fuel gas and a pressure sensor for measuring the intake pressure P A is arranged in the fuel gas line 2, and a pressure sensor for measuring the compressor outlet pressure P E is arranged in the discharge line 4.
  • These measuring devices are connected to the surge limit controller 15 via measuring lines 16, 17, 18. Furthermore, the pressure difference ⁇ P is determined at a throttle point at the compressor inlet. The throttle point is also connected to the surge limit controller 15 via a measuring line 19.
  • the fuel gas control valve 6 of the gas turbine 5 can be approximately 0.1 Second close. As a result, the fuel gas flow can also can be reduced from the nominal value to zero within this time. When the load is shed by the gas turbine 5 Generator must the fuel gas flow z. B. within 0.1 Seconds to a few percent. To the The gas turbine 5 must be able to continue operating Fuel gas pressure can be kept at the nominal value.
  • the Working point is the control line upstream of the surge limit to reach.
  • the surge limit control of the turbo compressor 3 now reacts to a further working point shift and opens the surge limit control valve 13 from the pressure side Suction side of the turbo compressor 3.
  • the Controller can respond is a corresponding increase in Fuel gas pressure the result.
  • the pressure may increase this way far that the gas turbine 5 completely for safety reasons must be switched off.
  • a known control method uses to keep the Compressor end pressure when reducing the load on the gas turbine 5 the surge limit valve 13.
  • the surge limit regulator 15 receives at this method, a final pressure limitation regulation, which at an increase in the compressor end pressure, the surge limit valve 13 opens in such a way that the final pressure is kept constant.
  • the setpoint of this final pressure control regulator is slightly above the target value of the final pressure regulator 20, so that this stationary the compressor inlet guide vanes 21 so wide concludes that the bypass valve is completely closed.
  • a function generator 24 (FNL 1920) the position of the fuel gas control valve 6, the mass flow through Fuel gas control valve 6 determined.
  • Has the fuel gas control valve 6 is a linear characteristic and is the pressure before and after Fuel gas control valve 6 constant (which is normally the case is not necessary to take these quantities into account become. If the fuel gas control valve 6 has a linear characteristic, is only the one in this function generator 24 (FNL 1920) Enter the course of a straight line. With non-linear characteristics can the course of the characteristic curve as a polyline or formula be saved.
  • are pressure or temperature before or after the fuel gas control valve 6 variable by Taking into account these sizes from the known Dimensioning equations for control valves the current Mass flow can be calculated.
  • the volume flow in the compressor inlet is calculated by multiplication by the compressor intake temperature T A and division by the intake pressure P A.
  • a scaling factor for adapting the measuring range can be inserted in an amplifier 27 (GAI 1923).
  • Another function generator 28 determines the course of the surge limit or the control line (blow-by line, blow-off line) of the surge limit controller 15 from the enthalpy difference ⁇ h.
  • the enthalpy difference is calculated as a function of the compressor outlet pressure P E , the suction pressure P A and the suction temperature T A in the surge limit controller 15 and is available there.
  • the output of amplifier 27 (GAI 1923) describes the Intake volume flow that occurs in the compressor inlet, if the current driving style until reaching the stationary one Condition remains.
  • the output of the function generator 28 (FNL 1924) describes the associated flow at the Surge limit or at the control line. From the difference of this Both variables can be determined whether the turbo compressor 3 can promote the flow to the gas turbine 5 without blowing or not. Is the flow (output of amplifier 27 (GAI 1923)) greater than the flow at the surge line (Output of function generator 28 (FNL 1924)) is not an action required.
  • a limiter 29 (LIM 1925) has a limiting function. He only lets negative values pass and limits positive values to zero. This means that a control variable is only generated if the difference is negative, i.e. the surge limit control valve 13 must open to keep the turbo compressor 3 stable in the map to be able to operate.
  • the flow through the surge limit control valve 13 is essentially determined by the position of the surge limit control valve 13 and the pressure upstream of the surge limit control valve 13.
  • the pressure upstream of the surge limit control valve 13 is largely identical to the compressor end pressure.
  • An amplifier 30 (GAI 1926) permits a scaling that may be required, and a multiplier 31 (MUL 1927) and a divider 32 (DIV 1928) determine a determination of the associated mass flow by multiplication by the suction pressure P A and division by the suction temperature T A.
  • a multiplier 31 MUL 1927
  • a divider 32 DIV 1928
  • the characteristic curve of the surge limit control valve 13 should be non-linear be or pressure or temperature before or after Surge valve can be variable by using the known dimensioning equations for control valves required opening of the surge limit control valve 13 determined become.
  • the tax variable can either be direct and only the Determine the position setpoint for the surge limit control valve 13.
  • This method has the advantage that the turbo compressor 3 is always driven at the same working point and thus it is ensured that the fuel gas pressure in the outlet of the turbo compressor 3 is always kept constant.
  • a method is preferred in which the Control variable acts in addition to the surge limit controller 15 and the Control variable either the output of the surge limit controller 15 is added or on one of the described below Assign the controller control signal is impressed.
  • the control variable and the output signal of the surge limit controller 15 conventional design are added to each other, the sum Both sizes form the setpoint for the surge limit control valve 13. In such a procedure, additional Measures are prevented that the exit of the Pump limit controller 15 overridden.
  • Pump limit regulator 15 and Pump limit control valve 13 must have a corresponding Have signal range, e.g. B. 4 mA to 20 mA.
  • the value of 4 mA corresponds to the minimum output signal of the Pump limit controller 15 and the value of 20 mA the maximum Output signal. With a value of 4 mA this is Pump limit control valve 13 fully open, at a value of 20 mA completely closed.
  • the surge limit controller 15 By limiting measures in the exit the surge limit controller 15 ensures that the Manipulated variable of the surge limit controller 15 does not have the value of 20 mA can exceed and not fall below the value of 4 mA. It is not enough to limit the manipulated variable in the output, rather, it is the integral part of the surge limit controller 15 limit so that it stays with larger ones Control deviations always only assume values such that the Addition of integral part and proportional part the permissible Do not exceed or fall below limits.
  • One possible measure is to push the limits of the Integral part of the surge limit controller 15 always under such Taking into account the tax rate that the Limits can be reached, but not exceeded become.
  • Another option is to use the integral part of the Pump limit controller 15 in the event of a discrepancy between Track controller output and valve position so that the Deviation becomes zero. This is advantageously the case designed that the tracking only takes place if the difference between valve position and manipulated variable Limit exceeds. This ensures that the Integral part not even with incorrectly chosen limits impermissibly far from the position of the surge limit control valve 13 can deviate and thus ultimately the limitation of Valve actuator is selected as the only active limit.
  • tax figure is designed dynamically. Instead of moving the Working point closer to a new stationary working point to process a constant control variable at the surge limit, the tax variable is designed to be yielding. this happens by the yielding summation in the delay element 34 (PT1 1930) and summer 35 (SUM 1931).
  • Opening the suction pressure control valve 10 is a function of Pressure difference between pipeline pressure and compressor suction pressure and the flow through the suction pressure control valve 10. With decreasing mass flow at constant pressures Close the suction pressure control valve 10 when the mass flow increases have to open it. The pipeline pressure rises at a constant Mass flow, the suction pressure control valve 10 must close and open when pipeline pressure drops.
  • Pipeline pressure changes are usually slow, because a large storage volume is effective. Flow mass flow changes can quickly, i. H. With a gradient of 100% change in 0.1 seconds. According to the invention, the control behavior can be carried out quickly Disturbance to the gas turbine 5 also improved significantly here become. From the position of the fuel gas control valve 6 can be taking into account the pipeline pressure, the required Calculate the position of the suction pressure control valve 11 directly. The Final pressure regulator 20 no longer needs the entire fault to settle but only the remaining control error. For this purpose, the manipulated variable (controller output) and the Control signal added to each other.
  • the tax variable can also be dynamic Controller output can be added, as it is for the Pump limit controller 15 has been described.
  • the required opening of the bypass valve 8 is proportional to Opening the fuel gas control valve 6. Is that Fuel gas control valve 6 opened wide requires the gas turbine 5 a lot of fuel and the bypass valve 8 must be opened wide be the required pressure drop between pipeline pressure and required fuel gas pressure upstream of the gas turbine 5 to reach. The bypass valve must be activated when the fuel gas requirement drops Close 8 so that the flow rate is the same Pressure loss is generated. In addition, the Pipeline pressure has an impact on the opening of the bypass valve 8. The higher the pipeline pressure, the further it has to be Close bypass valve 8.
  • Fuel gas flow rate or position of the fuel gas regulator valve as well as pressures and temperatures upstream and downstream of the valves can be done in different ways.
  • a third option is the assignment matrix using the thermodynamic and fluidic To theoretically calculate data of all system components.
EP01104340A 2000-03-14 2001-02-23 Procédé pour le contrôle de pompage d' un turbo-compresseur Expired - Lifetime EP1134422B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10012380 2000-03-14
DE10012380A DE10012380A1 (de) 2000-03-14 2000-03-14 Verfahren zum Schutz eines Turbokompressors vor Betrieb im instabilen Arbeitsbereich

Publications (3)

Publication Number Publication Date
EP1134422A2 true EP1134422A2 (fr) 2001-09-19
EP1134422A3 EP1134422A3 (fr) 2002-06-19
EP1134422B1 EP1134422B1 (fr) 2006-04-26

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EP01104340A Expired - Lifetime EP1134422B1 (fr) 2000-03-14 2001-02-23 Procédé pour le contrôle de pompage d' un turbo-compresseur

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US (1) US6551068B2 (fr)
EP (1) EP1134422B1 (fr)
AT (1) ATE324524T1 (fr)
DE (2) DE10012380A1 (fr)
ES (1) ES2261284T3 (fr)

Cited By (2)

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CH700991A1 (de) * 2009-05-13 2010-11-15 Alstom Technology Ltd Verfahren zum betrieb einer gasturbinenanlage mit einer verdichterstation für gasförmigen brennstoff.
WO2019162872A1 (fr) * 2018-02-23 2019-08-29 Atlas Copco Airpower, Naamloze Vennootschap Procédé d'actionnement d'un système de compresseur et système de compresseur

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ITTO20030392A1 (it) * 2003-05-28 2004-11-29 Varian Spa Sistema di pompaggio per vuoto.
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ES2544745T3 (es) 2004-09-09 2015-09-03 Alstom Technology Ltd Instalación de suministro de gas para una turbina de gas y procedimiento de funcionamiento correspondiente
EP1659294B1 (fr) * 2004-11-17 2017-01-11 Mitsubishi Heavy Industries Compressor Corporation Unité de commande pour compresseur et installation à turbine à gaz avec une telle unité
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US20100275611A1 (en) * 2009-05-01 2010-11-04 Edan Prabhu Distributing Fuel Flow in a Reaction Chamber
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US9057028B2 (en) 2011-05-25 2015-06-16 Ener-Core Power, Inc. Gasifier power plant and management of wastes
US8850790B2 (en) 2011-07-22 2014-10-07 Honeywell International Inc. Gas turbine engine speed control system and method during maximum fuel flow
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US9534780B2 (en) 2012-03-09 2017-01-03 Ener-Core Power, Inc. Hybrid gradual oxidation
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US9017618B2 (en) 2012-03-09 2015-04-28 Ener-Core Power, Inc. Gradual oxidation with heat exchange media
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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH700991A1 (de) * 2009-05-13 2010-11-15 Alstom Technology Ltd Verfahren zum betrieb einer gasturbinenanlage mit einer verdichterstation für gasförmigen brennstoff.
EP2251534A1 (fr) * 2009-05-13 2010-11-17 Alstom Technology Ltd Procédé de fonctionnement d'une turbine à gaz utilisant un compresseur de carburant gazeux
US8776528B2 (en) 2009-05-13 2014-07-15 Alstom Technology Ltd. Method for operating a gas turbine plant with a compressor station for gaseous fuel
WO2019162872A1 (fr) * 2018-02-23 2019-08-29 Atlas Copco Airpower, Naamloze Vennootschap Procédé d'actionnement d'un système de compresseur et système de compresseur
BE1026036B1 (nl) * 2018-02-23 2019-09-20 Atlas Copco Airpower Nv Werkwijze voor het aansturen van een compressorinrichting en compressorinrichting
CN111699321A (zh) * 2018-02-23 2020-09-22 阿特拉斯·科普柯空气动力股份有限公司 用于致动压缩机系统的方法以及压缩机系统
CN111699321B (zh) * 2018-02-23 2022-03-01 阿特拉斯·科普柯空气动力股份有限公司 用于致动压缩机系统的方法以及压缩机系统

Also Published As

Publication number Publication date
ES2261284T3 (es) 2006-11-16
EP1134422B1 (fr) 2006-04-26
DE10012380A1 (de) 2001-09-20
DE50109582D1 (de) 2006-06-01
ATE324524T1 (de) 2006-05-15
US20010022938A1 (en) 2001-09-20
US6551068B2 (en) 2003-04-22
EP1134422A3 (fr) 2002-06-19

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